Aircraft propulsion system and method for operating such a system

Patent metadata

Field	Value
Publication number	US-12583610-B2
Application number	US-201917292658-A
Country	US
Kind code	B2
Filing date	Nov 19, 2019
Priority date	Nov 22, 2018
Publication date	Mar 24, 2026
Grant date	Mar 24, 2026

Abstract

The invention relates to a propulsion system intended to be mounted on an aircraft comprising a main body, said propulsion system comprising: —a first rotating propulsive member and a second rotating propulsive member that are intended to be mounted on either side of said main body, —a transmission housing connected to the first rotating propulsive member via a first mechanical shaft and to the second rotating propulsive member via a second mechanical shaft, —a single gas generator connected to said transmission housing and configured to rotate the first rotating propulsive member and the second rotating propulsive member, and—a single auxiliary turbomachine configured to rotate the first rotating propulsive member and the second rotating propulsive member independently of the gas generator.

First claim

The invention claimed is:

1 . A propulsion system for mounting on an aircraft comprising a main body, said propulsion system comprising:
a first rotating propulsive member and a second rotating propulsive member, the first and second rotating propulsive members adopted for mounting on either side of said main body; a transmission box connected to the first rotating propulsive member via a first mechanical shaft and to the second rotating propulsive member via a second mechanical shaft; a single gas generator comprising a compressor, a combustion chamber, and a turbine, the single gas generator is configured to produce a thrust of X-Newtons (N) and operatively connect to said transmission box to rotatably drive the first rotating propulsive member and the second rotating propulsive member; a single auxiliary turbomachine connected to the transmission box via a clutch; wherein the single auxiliary turbomachine has two operating modes during flight to rotate the first and second rotating propulsive members, including a first operating mode in which the single gas generator is running and a second operating mode in which the single gas generator is cut off; and wherein the single auxiliary turbomachine, when operating, is sized to generate thrust that is less than the thrust of the X-N generated by the single gas generator, wherein the X-N is a numerical value, and the single auxiliary turbomachine is sized to generate thrust of between about 5%-20% of the X-N.

2 . The propulsion system according to claim 1 , wherein the single auxiliary turbomachine is an auxiliary power unit (APU) that is arranged to power light and air condition when the aircraft is on a ground and the single gas generator is cut off.

3 . A propulsion system for mounting on an aircraft comprising a main body, said propulsion system comprising:
a first rotating propulsive member and a second rotating propulsive member, the first and second rotating propulsive members adopted for mounting on either side of said main body; a transmission box connected to the first rotating propulsive member via a first mechanical shaft and to the second rotating propulsive member via a second mechanical shaft; a single gas generator comprising a compressor, a combustion chamber, and a turbine, the single gas generator is configured to produce a thrust of X-Newtons (N) and operatively connect to said transmission box to rotatably drive the first rotating propulsive member and the second rotating propulsive member; a single auxiliary turbomachine connected to an electric generator that powers a motor and the motor is operatively connected to at least one of the first rotating propulsive member and the second rotating propulsive member; wherein the single auxiliary turbomachine has two operating modes during flight to rotate the first and second rotating propulsive members, including a first operating mode in which the single auxiliary turbomachine is operating and the single gas generator is running and a second operating mode in which the single auxiliary turbomachine is operating and the single gas generator is cut off; wherein the single auxiliary turbomachine, when operating, is sized to generate thrust that is less than the thrust of the X-N generated by the single gas generator, and wherein the X-N is a numerical value; and wherein the motor is directly connected to the transmission box to directly drive the transmission box and the single auxiliary turbomachine is sized to generate thrust of between about 5%-20% of the X-N.

4 . The propulsion system according to claim 3 , wherein the single auxiliary turbomachine is an auxiliary power unit (APU) that is arranged to power light and air condition when the aircraft is on a ground and the single gas generator is cut off.

5 . The propulsion system according to claim 3 , wherein the single auxiliary turbomachine is connected to the electric generator and the motor is connected to a clutch, which is connected to the transmission box.

6 . The propulsion system according to claim 3 , wherein the single auxiliary turbomachine is connected to the electric generator and the motor directly drives the first mechanical shaft that powers the first rotating propulsive member, the second mechanical shaft that powers the second rotating propulsive member or a mechanical shaft that powers both the first and second rotating propulsive members.

Assignees

• Safran Aircraft Engines

Inventors

• Parmentier Nicolas Claude
• Missout Marc

Classifications

• B64D35/023

  of series-parallel type · CPC title

• B64D27/357

  using batteries · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D27/026

  comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33) · CPC title

• B64D27/14

  within, or attached to, fuselages · CPC title